System for initiating ordnance devices mounted upon a rotating plate

ABSTRACT

A system for the sequential transfer of lineal mechanical force to initiate ordnace detonators mounted upon a rotating plate, for example a system to sequentially detonate for the purpose of severing helicopter blades, so as to enable helicopter pilot ejection under emergency conditions.

United States Patent 11 1 Ingham et al.

1451 Dec. 11, 1973 SYSTEM FOR INITIATING ORDNANCE DEVICES MOUNTED UPON AROTATING PLATE [75] Inventors: Robert W. Ingham; Milton W.

1 Chambers, both of Hollister, Calif.

[73] Assignee: Teledyne McCormick Selph,

Hollister, Calif.

[22] Filed: Feb. 16, 1972 121 Appl. NO.: 226,878

[52] U.S. Cl. 244/17.l1, 89/1 B [51] Int. Cl. B64c 27/00 [58] Field ofSearch 102/24 HC; 89/1 B,

[56] References Cited UNITED STATES PATENTS 3,229,931 Larsen 244/l7.ll

Baker et al 102/24 HC Archbold 89/12 Primary Examiner-Trygve M. BlixAssistant Examiner--Paul E. Sauberer Att0rneyDavid l-l. Semmes 57 nABSTRACT A system for the sequential transfer of lineal mechanical forceto initiate ordnace detonators mounted upon a rotating plate, forexample a system to sequentially detonate for the purpose of severinghelicopter blades, so as to enable helicopter pilot ejection under emergency conditions.

15 Claims, 6 Drawing Figures PAIENIEDUEC H ma 3,778,008

- sum 3 c; 4

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SYSTEM FOR INITIATING ORDNANCE DEVICES MOUNTED UPON A ROTATING PLATEBACKGROUND OF THE INVENTION 1. Field of the Invention Previously, therehas not been provided an emergency: procedure for ejection of helicopterpilots in the event of an in-flight emergency. The rotating helicopterblades precluded pilot ejection. If randomly severed they pose a dangerto nearby formation helicopters. Therefore, little, if any, attentionhas been given to sequentially severing the helicopter blades, so as toenable precise directional trajectories of the removed blades to avoidstriking other helicopters in the same formation.

SUMMARY OF THE INVENTION The present application relates to a method forsequential initiation of ordnance devices on a rotating plate ormechanism. A contemporary problem in the aerospace industry is the meansby which rotating ordnance initiated systems can be sequentially firedfrom a stationary point. Such a requirement exists on helicopter orother systems (employing a combination of fixed and rotationalmechanisms) for transmitting deto nation output to the rotor head forseverance action of the blades in a precise and predicted ejectiontrajectory awayifrom helicopters flying the same formation.

The invention consists of ordnance devices attached to a rotatingmechanism and fired by a system of linear actuators and cams. The systemis initiated by propagating. a detonating shock through a confineddetonating fuse or shielded mild detonating cord and displacing thelinear actuator with firing pin assembly 1 into thepath of the fixed cam4 located on the rotating plate 5.See FIGS. 1 and 2.

The fixed cam 4 mounted on the rotating plate is located directly overthe intended firing point to start the ignition sequence. As the fixedcam 4 on the rim of the rotor plate 5 strikes the cam follower 26 on thefiring pin assembly 1 the sequence of events results in shearing of thesafety pin 12 and instant compression of the spring 14 against thefiring pin shaft assembly as shown in FIG. 3. At a pre-determined pointthe ball detent 16 in FIG. 3, is disengaged andthe firing pin 20 isreleased with a constant spring force that initiates the primer 17 inFIG. 3, thus igniting the explosive train in the output end of the unit.A detonation shock wave is then transferred into and detonationcontinued by the engaged SMDC (shielded mild detonating cord) or CDF(confined detonating fuse) to the second linear actuator and sliding cam9 in FIG. 1 located 0: degrees ahead of the first linear actuator 1. Thesequentially fired sliding cam 9 is located in the stationary outer ring27 and is moved into functioning position by an impulse or gasoperatedpiston 8 actuated by the interconnection CDF or SMDC assembly 7. One ormore multispaced actuator stations6 are provided on the rotating innerring. Each station contains a firing pin initiated detonator assemblythat is positively initiated by the repositioned cam 9 on the fixedplate.

The same firing sequence is repeated when the cam follower (roller) onthe end of the rotating plate mounted firing pin assembly 6 is driveninward by the linear actuated cam 9 the sequence of events results in:l) shearing of the safety pin 12, and (2) instant compression of spring14 against the firing pin shaft assembly. At a pre-determined point, theball detents 16 are again disengaged and the firing pin 20 is releasedwith a constant spring that initiates primer 17, thus initiating theexplosive train in the output end of the firing pin assembly. The samefiring sequence repeats for each succeeding station 6 as it passesacross the face of the cam 9.

Ignition of all firing pin assemblies would be complete in onerevolution of the rotating base 5. By this means a series of detonationoutput assemblies 6 mounted on rotating plates can be accurately firedfrom a gas or impulse operated cam on a fixed plate 27. Once initiated,these assemblies provide a means of propagating detonation shockstimulus to their respective end termination.

In the ensuing description, the term detonation" is used generically tocomprehend also a deflagration reaction.

Accordingly, it is an object of this invention to provide a method forignition of sequential detonation on a rotating plate from a fixed gasor impulse operated cam on a stationary plate.

Another object of the invention is to provide the neeessary mechanism bywhich location of first ignition" on the rotating plate may bepre-determined.

Yet, additional objects of the invention will become apparent from thespecifications and attached drawings wherein:

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a fragmentary perspective,showing positioning of the helicopter rotating plate supporting a seriesof radially mounted ordnance devices and an adjacent stationary platemounting first and second linear actuators;

FIG. 2 is a fragmentary elevation, partially in section, through thestationary plate showing superposition of the first and second linearactuator elements and adjacent the helicopter rotating plate, supportingthe stationary cam and radially positioned ordnance devices;

FIG. 3 is a vertical section of a single radially positioned ordnancedevice, showing the cam responsive means, compression means, firing pinand explosive train;

FIG. 4 is a fragmentary section of the linear assembly, illustrated inFIG. 3, showing the firing pin released from the ball detent foractuation of the explosive train which, in turn, detonates the explosivecutting device located around the individual helicopter blades;

FIG. 5 is a fragmentary, enlarged elevation, partially in section,showing the stationary plate first linear actuator and its relatedfiring pin assembly extensible into the path of the rotating platestationary cam; and

FIG. 6 is an enlarged, fragmentary elevation, partially in section,showing the second linear actuator, including the chamber, and linearlyaligned piston and sliding cam element extensible into the path of theordnance devices mounted upon the rotating plate.

DESCRIPTION OF THE PREFERRED EMBODIMENTS In FIG. 1 there is illustrateda suggested sequential firing assembly comprising a linear actuator andfiring pin assembly I mounted in a track to a fixed plate 2. Initiationby detonation input energy from CDF or SMDC 3 causes the first linearactuator assembly 1 to move into the path of the rotating cam 4 mountedupon the periphery of the rotating plate 5. The location of cam 4pre-determines the first firing pin assembly 6 to be fired in thesequence system, in this case A. When cam 4 strikes firing pin assembly1 and related firing pin assembly 6 a detonation output fires into theCDF or SMDC 7 and propagates into the second linear actuator 8 whichdrives cam 9 into the arc of the cam follower 10 attached to each firingpin assembly 6 which is mounted upon rotating plate 5. Angle a betweenfirst linear actuator assembly 1 and second linear actuator assembly 8represents the arc subtended by the firing pin assembly 6 when therotating cam 4 first repositions to fire each firing pin assembly 6.

As illustrated in FIGS. 1 and 3 angle B is the angle between each firingpin assembly 6 mounted upon rotating plate that can be pre-determined toinitiate a detonation output through connecting CDF or SMDC 11 to areceptor such as cartridge actuated devices or flexible linear shapedcharges. In FIG. 1, firing pin assembly 6 designated A and mounted uponrotating plate 5 will always be the first sequentially fired ordnancedevice by the second linear actuator 8 and cam 9.

In FIG. 2 there is illustrated the relative position of the rotating cam4 in line with the first linear actuator assembly 1 and its relatedfiring pin assembly 6. SMDC or CDF 3 is shown attached to the firstlinear actuator assembly 1 and drives cam 9 into position to depressroller cam followers into each of the firing pin assemblies 6, (A, B,C", and D"). As plate 5 rotates each firing pin assembly 6 issequentially fired by cam 9.

In FIG. 3 there is illustrated the longitudinal cross section of eachfiring pin assembly 6 which is mounted upon rotating plate 5. The safetypin 12 is sheared when the cam roller follower 10 is driven into body 13compressing the spring 14 and uncovering the port 27 in the firing pinsleeve 15 to release and strike the primer 17. A suggested explosivetrain, consisting of lead azide l8 and RDX 19, produces a detonationoutput capable of intiating SMDC or CDF 11.

In FIG. 4 there is shown a similar longitudinal section of the firingpin assembly 6 when the ball detent 16 has been displaced through theuncovered port 27 in the firing pin sleeve 15 and the firing pin 20released to strike the primer 17.

In FIG. 5 there is illustrated the linear actuated assembly 1 with asimilar firing pin assembly 6' mounted on top ofa sliding base 21. WhenSMDC or CDF 3 detonates, the output energy actuates sliding base 21 intrack 22 a distance equivalent to D. The linear displacement of thesliding base 21 positions firing pin assembly 6 and its follower 26 tobe impacted by the rotating cam 4. A simple ball detent 24 keeps thehousing locked in the fully extended position, as well as in the unfiredposition.

In FIG. 6 there is illustrated second linear reactor 8 fired by CDF 7,so as to drive aligned piston 23 and related sliding cam element 9 intothe path of the cam followers 10. Cam followers 10 are thus depressedinto each of the firing pin assemblies 6. A ball detent 25 may be usedto lock together the cam components.

We claim:

1. System for initiating ordnance devices mounted upon a rotating platecomprising:

A. a series of radially positioned ordnance devices mounted upon saidrotating plate including:

i. a shock responsive element which protrudes beyond the periphery ofthe plate, and

ii. a detonation element extending inwardly of said plate;

B. a stationary cam mounted upon said plate, so as to extend beyond theperiphery;

C. a first linear actuator mounted upon a stationary base adjacent saidrotating plate and including i. a firing pin assembly,

ii. a first shock responsive element connected to and actuated by saidfiring pin assembly so as to protrudeinto the path of said stationarycam, as said plate rotates;

D. a second linear actuator mounted upon said stationary base adjacentsaid rotating plate and including:

i. a second shock responsive element connected to said first shockresponsive element in said first linear reactor actuator and ii. asliding cam extensible upon detonation action into the rotating arc ofsaid radially positioned ordnance devices mounted upon said rotatingplate.

2. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 1, said rotating plate being mounted upon a mainhelicopter rotor shaft and extending below rotor head and bladearticulation mechanisms.

3. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 2, each of said ordnance devices mounted upon saidplate being attached to a helicopter rotor shaft, such that a detonatingshock may be propagated, so as to sequentially sever the helicopterblades.

4. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 3, whrein confined detonating fuse is used within saidfirst linear reactor to advance said first shock responsive element intothe path of said cam.

5. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 4, wherein confined detonating fuse is used totransmit shock from said first shock responsive element to said secondshock responsive element in said second linear actuator, so as to extendsaid sliding cam into the rotating of arc of said radially positionedordnance devices.

6. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 5, wherein said radially positioned ordnance devicemounted upon said rotating plate includes:

1'. a rotatable cam follower, extending beyond the periphery of saidplate;

ii. a firing pin;

iii. a lineal compressive member interconnecting said rotatable cam andsaid firing pin, and

iv. an explosive train actuable by means of lineal movement of saidfiring pin and said compressive member, including a confined detonatingfuse leading from said explosive train inwardly of said rotating plate.

7. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 6, wherein said confined detonating fuse leads fromsaid explosive train to each of said helicopter blades.

8. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 7, wherein said first lineal actuator firing pinassembly further includes: a

" gas discharge and firing pin, a sliding base and cam follower andlinearly aligned, such that linear actuation of said firing pin [inearly advances said cam follower into the path of said stationary cammember mounted upon said rotating plate.

9. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 8, wherein said second linear. actuator sliding camfurther includes:

i. a cylinder,

ii. a gas discharge mechanism,

iii. a confined detonating fuse leading from said first shock responsiveelement in said first linear actuator into said gas discharge mechanism,

iv..a sliding piston actuable within said cylinder by v. a sliding cammounted abutting said piston and extensible into the rotating arc ofsaid rotatable cam follower mounted upon said rotating plate.

10. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 9, wherein said rotatable cam followers and saidsliding cam mounted upon said stationary base are coextensive.

1 l. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 10, wherein said stationary cam and said rotatable camfollowers mounted upon said rotating plate are coextensive peripherallyoutwardly of said rotating plate.

12. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 11, wherein each of said radially positioed ordnancedevices includes a ball detent member locking said lineal compressivememher in extended position radially outwardly of said plate, as saidexplosive train is actuated.

13. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 12, wherein the first linear actuator and said secondlinear actuator are disposed at an angle a therebetween which representsthe arc subtended by the rotatable cam follower as it repositions tofire each firing pin assembly.

14. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 12, wherein the rotating plate mounted firing pinassemblies are spaced by an angle B which represents the distancetherebetween and can be predetermined.

15. In a helicopter of the type having a hollow rotor shaft and aplurality of helicopter blades'atta'ched to the shaft, a bladedestruction system comprising:

A. a rotating plate rotatable with said rotor shaft and mounting aplurality of radially positioned shock responsive elements protrudingbeyond the periphery thereof;

B. an individual detonation train leading from each shock responsiveelement to each said helicopter blade, and

C. cam means independently positioned apart from said rotating plate andlinearly extensible into the rotating plane of said shock responsiveelements mounted on said rotating plate to actuate said shock responsiveelements and thereby said detonation trains to detonate and sever saidhelicopter blades.

1. System for initiating ordnance devices mounted upon a rotating platecomprising: A. a series of radially positioned ordnance devices mountedupon said rotating plate including: i. a shock responsive element whichprotrudes beyond the periphery of the plate, and ii. a detonationelement extending inwardly of said plate; B. a stationary cam mountedupon said plate, so as to extend beyond the periphery; C. a first linearactuator mounted upon a stationary base adjacent said rotating plate andincluding i. a firing pin assembly, ii. a first shock responsive elementconnected to and actuated by said firing pin assembly so as to protrudeinto the path of said stationary cam, as said plate rotates; D. a secondlinear actuator mounted upon said stationary base adjacent said rotatingplate and including: i. a second shock responsive element connected tosaid first shock responsive element in said first linear reactoractuator and ii. a sliding cam extensible upon detonation action intothe rotating arc of said radially positioned ordnance devices mountedupon said rotating plate.
 2. A system for initiating ordnance devicesmounted upon a rotating plate as in claim 1, said rotating plate beingmounted upon a main helicopter Rotor shaft and extending below rotorhead and blade articulation mechanisms.
 3. A system for initiatingordnance devices mounted upon a rotating plate as in claim 2, each ofsaid ordnance devices mounted upon said plate being attached to ahelicopter rotor shaft, such that a detonating shock may be propagated,so as to sequentially sever the helicopter blades.
 4. A system forinitiating ordnance devices mounted upon a rotating plate as in claim 3,whrein confined detonating fuse is used within said first linear reactorto advance said first shock responsive element into the path of saidcam.
 5. A system for initiating ordnance devices mounted upon a rotatingplate as in claim 4, wherein confined detonating fuse is used totransmit shock from said first shock responsive element to said secondshock responsive element in said second linear actuator, so as to extendsaid sliding cam into the rotating of arc of said radially positionedordnance devices.
 6. A system for initiating ordnance devices mountedupon a rotating plate as in claim 5, wherein said radially positionedordnance device mounted upon said rotating plate includes: i. arotatable cam follower, extending beyond the periphery of said plate;ii. a firing pin; iii. a lineal compressive member interconnecting saidrotatable cam and said firing pin, and iv. an explosive train actuableby means of lineal movement of said firing pin and said compressivemember, including a confined detonating fuse leading from said explosivetrain inwardly of said rotating plate.
 7. A system for initiatingordnance devices mounted upon a rotating plate as in claim 6, whereinsaid confined detonating fuse leads from said explosive train to each ofsaid helicopter blades.
 8. A system for initiating ordnance devicesmounted upon a rotating plate as in claim 7, wherein said first linealactuator firing pin assembly further includes: a firing pin, a slidingbase and cam follower and linearly aligned, such that linear actuationof said firing pin linearly advances said cam follower into the path ofsaid stationary cam member mounted upon said rotating plate.
 9. A systemfor initiating ordnance devices mounted upon a rotating plate as inclaim 8, wherein said second linear actuator sliding cam furtherincludes: i. a cylinder, ii. a gas discharge mechanism, iii. a confineddetonating fuse leading from said first shock responsive element in saidfirst linear actuator into said gas discharge mechanism, iv. a slidingpiston actuable within said cylinder by gas discharge and v. a slidingcam mounted abutting said piston and extensible into the rotating arc ofsaid rotatable cam follower mounted upon said rotating plate.
 10. Asystem for initiating ordnance devices mounted upon a rotating plate asin claim 9, wherein said rotatable cam followers and said sliding cammounted upon said stationary base are coextensive.
 11. A system forinitiating ordnance devices mounted upon a rotating plate as in claim10, wherein said stationary cam and said rotatable cam followers mountedupon said rotating plate are coextensive peripherally outwardly of saidrotating plate.
 12. A system for initiating ordnance devices mountedupon a rotating plate as in claim 11, wherein each of said radiallypositioed ordnance devices includes a ball detent member locking saidlineal compressive member in extended position radially outwardly ofsaid plate, as said explosive train is actuated.
 13. A system forinitiating ordnance devices mounted upon a rotating plate as in claim12, wherein the first linear actuator and said second linear actuatorare disposed at an angle Alpha therebetween which represents the arcsubtended by the rotatable cam follower as it repositions to fire eachfiring pin assembly.
 14. A system for initiating ordnance devicesmounted upon a rotating plate as in claim 12, wherein the rotating platemounted Firing pin assemblies are spaced by an angle B which representsthe distance therebetween and can be predetermined.
 15. In a helicopterof the type having a hollow rotor shaft and a plurality of helicopterblades attached to the shaft, a blade destruction system comprising: A.a rotating plate rotatable with said rotor shaft and mounting aplurality of radially positioned shock responsive elements protrudingbeyond the periphery thereof; B. an individual detonation train leadingfrom each shock responsive element to each said helicopter blade, and C.cam means independently positioned apart from said rotating plate andlinearly extensible into the rotating plane of said shock responsiveelements mounted on said rotating plate to actuate said shock responsiveelements and thereby said detonation trains to detonate and sever saidhelicopter blades.